GOE 574 AIRFOIL (goe574-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 574 AIRFOIL (goe574-il) Reynolds number: 100,000 Max Cl/Cd: 55.97 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe574-il-100000.txt Download as CSV file: xf-goe574-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 574 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3390 0.10370 0.09933 -0.0326 1.0000 0.0657
-7.750 -0.3553 0.10268 0.09842 -0.0324 1.0000 0.0661
-7.500 -0.3693 0.10138 0.09724 -0.0331 1.0000 0.0664
-7.250 -0.3798 0.09971 0.09564 -0.0344 1.0000 0.0666
-7.000 -0.3738 0.09386 0.08989 -0.0295 1.0000 0.0680
-6.750 -0.3694 0.09081 0.08688 -0.0253 1.0000 0.0703
-6.500 -0.3776 0.08896 0.08512 -0.0231 1.0000 0.0718
-6.250 -0.3887 0.08740 0.08363 -0.0210 1.0000 0.0730
-6.000 -0.3998 0.08582 0.08213 -0.0194 1.0000 0.0746
-5.750 -0.3661 0.08263 0.07858 -0.0382 0.9894 0.0807
-5.500 -0.3501 0.07616 0.07230 -0.0358 0.9856 0.0833
-5.250 -0.3205 0.07209 0.06817 -0.0401 0.9763 0.0907
-5.000 -0.2893 0.06704 0.06299 -0.0471 0.9655 0.0990
-4.750 -0.2556 0.06252 0.05824 -0.0542 0.9540 0.1112
-4.500 -0.2214 0.05891 0.05432 -0.0598 0.9423 0.1244
-4.250 -0.1963 0.05471 0.05024 -0.0604 0.9338 0.1321
-4.000 -0.1588 0.05092 0.04616 -0.0653 0.9251 0.1501
-3.500 -0.1020 0.04452 0.03939 -0.0694 0.9020 0.1974
-3.250 -0.0720 0.04107 0.03595 -0.0704 0.8930 0.2177
-2.500 0.0674 0.02776 0.02017 -0.0782 0.8706 0.1047
-2.250 0.1082 0.02512 0.01674 -0.0790 0.8599 0.0936
-2.000 0.1570 0.02296 0.01410 -0.0822 0.8509 0.0957
-1.750 0.2154 0.02091 0.01166 -0.0875 0.8421 0.0955
-1.500 0.2666 0.01924 0.00989 -0.0917 0.8285 0.0982
-1.250 0.3171 0.01822 0.00876 -0.0959 0.8131 0.1066
-1.000 0.4982 0.01400 0.00695 -0.1277 0.7991 1.0000
-0.750 0.5320 0.01417 0.00668 -0.1287 0.7768 1.0000
-0.500 0.5637 0.01438 0.00652 -0.1294 0.7569 1.0000
-0.250 0.5930 0.01460 0.00645 -0.1296 0.7394 1.0000
0.000 0.6166 0.01486 0.00650 -0.1287 0.7228 1.0000
0.250 0.6412 0.01513 0.00656 -0.1280 0.7086 1.0000
0.500 0.6669 0.01540 0.00662 -0.1276 0.6964 1.0000
0.750 0.6884 0.01569 0.00680 -0.1263 0.6843 1.0000
1.000 0.7105 0.01600 0.00700 -0.1252 0.6734 1.0000
1.250 0.7346 0.01630 0.00719 -0.1245 0.6641 1.0000
1.500 0.7584 0.01661 0.00740 -0.1238 0.6554 1.0000
1.750 0.7799 0.01698 0.00772 -0.1226 0.6472 1.0000
2.000 0.8050 0.01731 0.00797 -0.1222 0.6406 1.0000
2.250 0.8256 0.01772 0.00841 -0.1209 0.6335 1.0000
2.500 0.8495 0.01808 0.00873 -0.1203 0.6272 1.0000
2.750 0.8713 0.01851 0.00915 -0.1192 0.6212 1.0000
3.000 0.8922 0.01894 0.00962 -0.1180 0.6152 1.0000
3.250 0.9187 0.01934 0.00999 -0.1179 0.6108 1.0000
3.500 0.9354 0.01990 0.01068 -0.1160 0.6051 1.0000
3.750 0.9570 0.02037 0.01120 -0.1150 0.5999 1.0000
4.000 0.9841 0.02080 0.01163 -0.1150 0.5959 1.0000
4.250 0.9978 0.02148 0.01248 -0.1126 0.5907 1.0000
4.500 1.0179 0.02203 0.01315 -0.1113 0.5858 1.0000
4.750 1.0454 0.02245 0.01360 -0.1113 0.5816 1.0000
5.000 1.0564 0.02313 0.01447 -0.1083 0.5748 1.0000
5.250 1.0846 0.02331 0.01467 -0.1082 0.5678 1.0000
5.500 1.1011 0.02343 0.01487 -0.1057 0.5558 1.0000
5.750 1.1280 0.02281 0.01416 -0.1045 0.5373 1.0000
6.000 1.1431 0.02258 0.01397 -0.1014 0.5204 1.0000
6.250 1.1600 0.02239 0.01382 -0.0987 0.5043 1.0000
6.500 1.1753 0.02203 0.01347 -0.0955 0.4850 1.0000
6.750 1.1826 0.02156 0.01301 -0.0905 0.4596 1.0000
7.000 1.1840 0.02123 0.01267 -0.0845 0.4313 1.0000
7.250 1.1782 0.02105 0.01244 -0.0772 0.3951 1.0000
7.500 1.1697 0.02120 0.01254 -0.0697 0.3381 1.0000
7.750 1.1496 0.02232 0.01294 -0.0608 0.2324 1.0000
8.000 1.1247 0.02462 0.01451 -0.0524 0.1259 1.0000
8.250 1.1041 0.02692 0.01634 -0.0451 0.0744 1.0000
8.500 1.0962 0.02865 0.01808 -0.0399 0.0629 1.0000
8.750 1.0933 0.03018 0.01974 -0.0357 0.0576 1.0000
9.000 1.0899 0.03185 0.02158 -0.0319 0.0538 1.0000
9.250 1.0844 0.03378 0.02366 -0.0283 0.0517 1.0000
9.500 1.0775 0.03599 0.02603 -0.0252 0.0505 1.0000
9.750 1.0674 0.03868 0.02886 -0.0225 0.0494 1.0000
10.000 1.0605 0.04135 0.03165 -0.0204 0.0486 1.0000
10.250 1.0578 0.04378 0.03421 -0.0186 0.0479 1.0000
10.500 1.0577 0.04600 0.03655 -0.0167 0.0472 1.0000
10.750 1.0632 0.04771 0.03831 -0.0148 0.0462 1.0000
11.000 1.0757 0.04890 0.03950 -0.0126 0.0442 1.0000
11.250 1.0981 0.04965 0.04017 -0.0105 0.0417 1.0000
11.500 1.1647 0.04955 0.04001 -0.0094 0.0417 1.0000
12.250 1.3536 0.06493 0.05641 -0.0188 0.0495 1.0000
12.500 1.3346 0.06432 0.05609 -0.0120 0.0508 1.0000
12.750 1.3052 0.06550 0.05768 -0.0061 0.0519 1.0000
13.000 1.2824 0.06851 0.06115 -0.0020 0.0548 1.0000
13.250 1.3308 0.07879 0.07233 -0.0025 0.0851 1.0000
13.500 1.2986 0.08078 0.07457 0.0014 0.0847 1.0000
13.750 1.2655 0.08362 0.07763 0.0038 0.0843 1.0000
14.000 1.2353 0.08727 0.08150 0.0047 0.0839 1.0000
14.250 1.2059 0.09172 0.08614 0.0046 0.0838 1.0000
14.500 1.1796 0.09681 0.09139 0.0036 0.0839 1.0000
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Polar data table (+)
Polar graphs
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